公开(公告)号：WO2020261136A2

公开(公告)日：2020-12-30

申请号：PCT/IB2020/055963

申请日：2020-06-24

Applicant: WEIDEMANN, Hermann Arthur

Inventor： WEIDEMANN, Hermann Arthur

IPC: F42B10/22 ,  F42B10/24 ,  F42B10/26 ,  F42B14/00 ,  F42B14/02 ,  F42B14/04 ,  F42B10/38 ,  F42B5/02

Abstract: A bullet, having a longitudinal body on which is defined a set of radially spaced, longitudinally extending helical grooves corresponding to the rifling of a particular barrel and at least one circumferential drive band which intersects the set of helical grooves, to define a pressure retaining formation with a casing of a cartridge, in use.

公开(公告)号：WO2008010226A1

公开(公告)日：2008-01-24

申请号：PCT/IL2007/000916

申请日：2007-07-19

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD. ,  SHAI, Mordechai

Inventor： SHAI, Mordechai

IPC: F42B10/18 ,  F42B10/20 ,  F42B10/38 ,  F42B10/62 ,  B64C19/02 ,  B64C39/00 ,  B64C39/08

CPC classification number: F42B10/38 ,  B64C3/56 ,  B64C5/12 ,  B64C9/36 ,  B64C39/024 ,  B64C39/068 ,  B64C39/08 ,  B64C2201/102 ,  F42B10/18 ,  F42B10/20 ,  F42B10/62 ,  Y02T50/14

Abstract: A deployable wing arrangement or kit is provided for use with a longitudinally extending fuselage (20) having an upper portion and a lower portion. The kit includes a first pair of wings (100) pivotably mountable with respect to said upper portion and capable of being deployed from a first retracted position to a first deployed position, and a second pair of wings (102) pivotably mountable with respect to said lower portion and capable of being deployed from a second retracted position to a second deployed position. A strut arrangement, having at least one pair of struts (104), interconnect the first pair of wings (100) with the said second pair of wings (102). An air vehicle having such a kit, and a method for increasing the range of an air vehicle are also provided.

Abstract translation: 提供可展开的机翼装置或套件，用于具有上部和下部的纵向延伸的机身（20）。 该套件包括相对于所述上部可枢转地安装并且能够从第一缩回位置展开到第一展开位置的第一对翼（100），以及可相对于所述第一展开位置可枢转地安装的第二对翼 下部并且能够从第二缩回位置展开到第二展开位置。 具有至少一对支柱（104）的支柱装置将第一对翼（100）与所述第二对翼（102）互连。 还提供了一种具有这种套件的空中车辆，以及用于增加空中交通工具的范围的方法。

公开(公告)号：WO2007058573A2

公开(公告)日：2007-05-24

申请号：PCT/SE2006/001047

申请日：2006-09-14

Applicant: BAE SYSTEMS BOFORS AB ,  RÖNN, Torsten ,  PETTERSSON, Thomas ,  HEICHE, Ulf

Inventor： RÖNN, Torsten ,  PETTERSSON, Thomas ,  HEICHE, Ulf

IPC: F42B10/38 ,  F42B10/04 ,  F42B10/14 ,  F42B10/40 ,  F42B14/06

CPC classification number: F42B14/064 ,  F42B10/14 ,  F42B10/16 ,  F42B10/40 ,  F42B10/64

Abstract: The invention relates to a method for increasing the range of shells (1, 8, 13) charged with an explosive substance and other types of shell, which function as carriers of the one or other type of active payload. The method according to the invention thus provides an opportunity for increasing the range of fire of most types of artillery piece by increasing the muzzle velocity and the gliding flight capability of shells or projectiles fired from them, but without the need to increase the energy content in the propellant charges utilized for firing the shells or the projectiles concerned. The novelty proposed in accordance with the invention instead represents a radical modification to the design of the shell (1, 8, 13) utilized in conjunction therewith. The invention also relates to a shell charged with an explosive substance or provided with some other active payload which has been given a long range.

Abstract translation: 本发明涉及一种用于增加装有爆炸性物质的壳体（1,8,13）的范围和用作一种或其它类型的活性有效载荷的载体的其它类型的壳体的方法。 因此，根据本发明的方法提供了通过增加炮弹速度和从其发射的炮弹或射弹的滑行飞行能力而增加大多数类型火炮的火焰范围的机会，但是不需要增加其中的能量含量 用于发射炮弹或有关射弹的推进剂费用。 根据本发明提出的新颖性代替了与其结合使用的外壳（1,8和13）的设计的根本修改。 本发明还涉及一种装有爆炸性物质的壳体，或者具有一定距离范围内的一些其它有效载荷。

公开(公告)号：WO2023018744A1

公开(公告)日：2023-02-16

申请号：PCT/US2022/039880

申请日：2022-08-09

Applicant: FEDERAL CARTRIDGE COMPANY

Inventor： HURT, Richard ,  HEAD, Lawrence, P.

IPC: F42B12/78 ,  B21K21/10 ,  F42B5/28 ,  F42B12/02 ,  B21K21/06 ,  F42B10/32 ,  F42B10/38 ,  F42B10/42

Abstract: Devices and methods for a bullet with a strengthened mouth for improved penetration and expansion. In embodiments, a portion of the jacket is folded to provide double walls at the mouth. In embodiments, the jacket and core are partially bonded and partially separated. The core comprises a forward portion defining a cavity forming a hollow point of the bullet. The jacket comprising: a rearward cup portion, an ogive portion, an end portion, and a plurality of skives. The ogive portion is forward of the rearward cup portion. The end portion is directly adjacent the tip portion of the core, the end portion of the jacket curling radially inwardly toward the central axis. The plurality of skives are formed in the ogive portion of the jacket.

公开(公告)号：WO2018084391A1

公开(公告)日：2018-05-11

申请号：PCT/KR2017/003939

申请日：2017-04-12

Applicant: 주식회사 두레텍

Inventor： 김준규 ,  김형세

IPC: F42B10/38 ,  F42B10/46 ,  F42B10/44 ,  F42B33/00 ,  F15D1/00

Abstract: 본 발명은 유효사거리가 향상된 탄두에 관한 것으로, 반구 형상의 선단부(10)와; 상기 선단부(10)의 후단과 연결되면서 내측으로 오목한 곡면을 가지는 오목부(20)와; 상기 오목부(20)의 후단과 연결되면서 수평선을 기준으로 일정 각도(A)로 경사지게 형성되는 경사부(30)와; 상기 경사부(30)의 후단과 연결되면서 수평선을 기준으로 일정 각도(A')로 경사지게 형성되는 단턱부(40) 및; 상기 탄두의 후미 및 후단면에 걸쳐 형성되는 3개의 유체유도홈(50);으로 이루어지는 것을 특징으로 하며, 이러한 구성에 의해 본 발명은 탄두가 수중을 통과할 때 초공동 현상이 더욱 효과적으로 생성되면서 오랫동안 유지됨으로써 탄두의 유효 사거리가 대폭 향상된다.

Abstract translation: 本发明涉及具有改进的有效范围的弹头，包括：半球形末端部分; 连接到远端部分10的后端并具有向内凹陷的弯曲表面的凹部20; 连接到凹入部分20的后端并且相对于水平线以预定角度A倾斜的倾斜部分30; 台阶部分40连接到倾斜部分30的后端并且相对于水平线以预定角度A'倾斜; 根据本发明，当战斗部通过水时，更有效地产生超空泡，其中， 战斗部的有效射程得到了很大的改善。

公开(公告)号：WO2016204349A1

公开(公告)日：2016-12-22

申请号：PCT/KR2015/010973

申请日：2015-10-16

Applicant: 충남대학교산학협력단

Inventor： 안병권

IPC: F42B19/00 ,  F42B10/34 ,  F42B10/38 ,  B63B1/38

CPC classification number: B63B1/38 ,  F42B10/34 ,  F42B10/38 ,  F42B19/00 ,  Y02T70/122

Abstract: 본 발명은 압축공기탱크를 이용한 초월공동 수증운동체의 캐비테이터 시스템 에 관한 것이다. 본 발명에 따르면, 수중운동체의 배기가스가 아닌 압축공기탱크 내 부의 압축공기를 이용하여 공동을 형성하므로 이를 위한 환기시스템의 구성이 매우 간단해지며 나아가 압축공기의 온도, 압력, 성분 등의 특성이 균일하여 시간의 경과 에 따른 안정적인 초월공동의 형성이 가능해진다. 또한 수중운동체의 발사 초기에는 변환형 캐비테이터가 원뿔형상을 유지하므로 저항과 기진력을 줄일 수 있으며 속도 가 증가함에 따라 변환형 캐비테이터가 순차적으로 원판형상으로 변하며 이에 따라 발생하는 초월공동 형상도 커지기 때문에 수중운동체의 몸체 형상에 제한을 덜 받는다.

Abstract translation: 本发明涉及一种使用压缩空气罐的超高速水下航行器的气蚀系统。 根据本发明，空化不是通过使用水下航行器的排气而是通过在压缩空气罐内使用压缩空气而形成的，因此其通风系统的构造变得非常简单，此外，压缩空气的性质 例如温度，压力，物质等均匀，从而能够根据时间的流逝稳定地形成超空化。 此外，在水下航行器的发射的早期部分，转换型气蚀器保持圆锥形状，从而能够降低电阻和激励力，并且转换型气蚀器随着速度的增加而连续地变成圆盘形状 ，并且由此产生的超空化的形状也扩大，因此对水下车辆的身体形状的限制较少。

公开(公告)号：WO02014779A1

公开(公告)日：2002-02-21

申请号：PCT/SE2001/001330

申请日：2001-06-13

IPC: F42B10/14 ,  F42B10/40 ,  F42B15/10 ,  F42B10/38

CPC classification number: F42B10/14 ,  F42B10/40 ,  F42B15/105

Abstract: The present invention relates to an artillery missile (1) intended for firing on a ballistic trajectory, with gliding characteristics which can be put into effect, after it has reached the summit of this trajectory, to increase the maximum range of the missile. In order to obtain these gliding characteristics, the missile is provided with extendable aerodynamic bearing surfaces divided into firstly canard fins (5-8), which are retracted in the front part of the missile body and can be extended after the summit of trajectory, secondly main bearing surfaces (9, 10) made of resilient material, which, likewise during launching, are curved in against and around the central part (3) of the missile body in shallow recesses adapted thereto in the outer casing of the missile and which, after the summit of trajectory and being extended, form the wings (9, 10) of the missile, and thirdly stern fins, which, durign at least launching, are covered i the retracted position by a protective cover (14) in the rear part (4) of the missile.

Abstract translation: 本发明涉及一种用于在弹道轨迹上发射的炮弹（1），其具有可以在其达到该轨迹的​​顶点之后可以实施的滑翔特征，以增加导弹的最大射程。 为了获得这些滑翔特征，导弹设有可分开的第一扇翼（5-8）的伸缩空气动力轴承表面，它们缩回到导弹体的前部，并可在轨迹顶点后延伸，其次是 由弹性材料制成的主要支承表面（9,10），其同样在发射期间，在导弹本体的中心部分（3）上弯曲并围绕导弹本体的中部（3）弯曲并适应导弹外壳中的浅凹槽， 在轨迹顶点延伸之后，形成导弹的翼（9,10），第三尾鳍（至少发射）被后部的保护盖（14）覆盖在缩回位置 （4）导弹。

公开(公告)号：WO99066418A2

公开(公告)日：1999-12-23

申请号：PCT/US1999/000227

申请日：1999-01-06

IPC: F42B10/38 ,  F42B10/66 ,  F42B15/00 ,  G06F15/00

CPC classification number: F42B10/38 ,  F42B10/66 ,  F42B15/00

Abstract: A neural network controller (50) for a pulsed rocket motor tactical missile (10). The missile includes a fuselage or body (12), with a pulsed propulsion system (20). The pulsed propulsion system has a need for a logical control of the application of propulsion energy throughout the missle's flight. The controller (50) is trained to provide optimal initiation of individual rocket motor thrust pulses based on tactical information available at various points/times in the missle's flight. The controller training is through use of training cases, in which the network learns to output a specific target value(s) when specific values are input. When trained with a large sample of training cases selected from the multidimensional population of interest, the neural network effectively learns the correlations between inputs and outputs and can predict input/output relationships not previously seen in any traning case.

Abstract translation: 一种用于脉冲火箭发动机战术导弹（10）的神经网络控制器（50）。 导弹包括机身或机体（12），带有脉冲推进系统（20）。 脉冲推进系统需要对整个飞行中的推进能量的应用进行逻辑控制。 训练控制器（50），以基于在missle飞行中的各个点/次可用的战术信息来提供单独的火箭发动机推力脉冲的最佳启动。 控制器培训是通过使用培训案例，当具体值被输入时，网络学习输出特定的目标值。 在从多维感兴趣群体中选出的大量培训案例进行培训时，神经网络有效地学习了输入和输出之间的相关性，并且可以预测任何情况下以前没有的输入/输出关系。

公开(公告)号：WO2007058573A3

公开(公告)日：2008-03-20

申请号：PCT/SE2006001047

申请日：2006-09-14

Applicant: BAE SYSTEMS BOFORS AB ,  ROENN TORSTEN ,  PETTERSSON THOMAS ,  HEICHE ULF

Inventor： ROENN TORSTEN ,  PETTERSSON THOMAS ,  HEICHE ULF

IPC: F42B10/38 ,  F42B10/04 ,  F42B10/14 ,  F42B10/40 ,  F42B14/06

CPC classification number: F42B14/064 ,  F42B10/14 ,  F42B10/16 ,  F42B10/40 ,  F42B10/64

Abstract: The invention relates to a method for increasing the range of shells (1, 8, 13) charged with an explosive substance and other types of shell, which function as carriers of the one or other type of active payload. The method according to the invention thus provides an opportunity for increasing the range of fire of most types of artillery piece by increasing the muzzle velocity and the gliding flight capability of shells or projectiles fired from them, but without the need to increase the energy content in the propellant charges utilized for firing the shells or the projectiles concerned. The novelty proposed in accordance with the invention instead represents a radical modification to the design of the shell (1, 8, 13) utilized in conjunction therewith. The invention also relates to a shell charged with an explosive substance or provided with some other active payload which has been given a long range.

Abstract translation: 本发明涉及一种用于增加装有爆炸性物质的壳体（1,8,13）的范围和用作一种或其它类型的活性有效载荷的载体的其它类型的壳体的方法。 因此，根据本发明的方法提供了通过增加炮弹速度和从其发射的炮弹或射弹的滑行飞行能力来增加大多数类型火炮的火焰范围的机会，但不需要增加其中的能量含量 用于发射炮弹或有关射弹的推进剂费用。 根据本发明提出的新颖性代替了与其结合使用的壳（1,8,13）的设计的根本修改。 本发明还涉及一种装有爆炸性物质的壳体，或者具有一些已经被给予远距离的其它有效载荷。

公开(公告)号：WO02068896A2

公开(公告)日：2002-09-06

申请号：PCT/US0132639

申请日：2001-10-25

Applicant: ATLANTIC RES CORP ,  MISKELLY HERMANN L

Inventor： MISKELLY HERMANN L

IPC: F42B10/38 ,  F42B15/20 ,  F42B17/00 ,  F42B

CPC classification number: F42B10/38 ,  F42B15/20 ,  F42B17/00

Abstract: A supercavitating underwater projectile (10) adapted to be fired from a gun or the like, comprising a front end or nose portion (12) and a rear end portion (18). An auxilary rocket motor is disposed within the rear end portion (18) of the projectile (10) for providing additional thrust after the projectile (10) has been fired. Vents (28) are disposed within the projectile (10) and are in communication with the rocket motor and the exterior of the projectile (10) for venting some of the combustion gases from the rocket motor to the exterior of the projectile (10) near the nose portion (12) thereof to increase the size of the cavitation bubble formed as the projectile (10) travels through the water and thereby reduce hydrodynamic drag on the projectile.

Abstract translation: 一种适用于从枪等发射的超空腔水下射弹（10），包括前端或鼻部（12）和后端部分（18）。 辅助火箭发动机设置在射弹（10）的后端部分（18）中，用于在射弹（10）被击发之后提供额外的推力。 通风口（28）设置在射弹（10）内并且与火箭发动机和射弹（10）的外部连通，用于将一些燃烧气体从火箭发动机排放到射弹（10）的外部附近 其鼻部（12）用于增加随着射弹（10）穿过水而形成的空化气泡的尺寸，从而减少射弹上的流体动力学阻力。